Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e184-il-200000 Airfoil,e184-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,57.9864 Max Cl/Cd alpha,5 Url,http://airfoiltools.com/polar/csv?polar=xf-e184-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.250,-0.5498,0.09894,0.09617,0.0242,1.0000,0.0493 -9.000,-0.5499,0.09433,0.09158,0.0224,1.0000,0.0508 -8.750,-0.6564,0.09274,0.08981,0.0191,1.0000,0.0468 -8.500,-0.6512,0.08935,0.08644,0.0186,1.0000,0.0482 -8.250,-0.6529,0.08502,0.08215,0.0155,1.0000,0.0491 -8.000,-0.6584,0.08034,0.07750,0.0117,1.0000,0.0501 -7.750,-0.6601,0.07525,0.07239,0.0078,1.0000,0.0512 -7.500,-0.6595,0.06976,0.06683,0.0038,1.0000,0.0531 -7.250,-0.6641,0.06431,0.06078,-0.0019,1.0000,0.0572 -7.000,-0.6613,0.05657,0.05297,-0.0033,1.0000,0.0586 -6.750,-0.6442,0.05321,0.04971,-0.0034,1.0000,0.0605 -6.500,-0.6273,0.05042,0.04686,-0.0038,1.0000,0.0647 -5.500,-0.5503,0.02779,0.02203,-0.0040,1.0000,0.0405 -5.250,-0.5175,0.02287,0.01617,-0.0043,0.9646,0.0351 -5.000,-0.4879,0.02087,0.01376,-0.0042,0.9412,0.0346 -4.750,-0.4660,0.01938,0.01208,-0.0028,0.9213,0.0359 -4.500,-0.4448,0.01845,0.01098,-0.0012,0.9052,0.0380 -4.250,-0.4226,0.01729,0.00965,0.0005,0.8915,0.0386 -4.000,-0.3998,0.01625,0.00849,0.0019,0.8792,0.0396 -3.750,-0.3769,0.01539,0.00753,0.0033,0.8681,0.0415 -3.500,-0.3540,0.01471,0.00672,0.0047,0.8581,0.0442 -3.250,-0.3317,0.01381,0.00577,0.0060,0.8482,0.0509 -3.000,-0.3093,0.01269,0.00493,0.0071,0.8387,0.1082 -2.750,-0.2899,0.01150,0.00453,0.0083,0.8304,0.2866 -2.500,-0.2704,0.01061,0.00430,0.0098,0.8215,0.4526 -2.250,-0.2543,0.00965,0.00419,0.0124,0.8134,0.6560 -2.000,-0.1795,0.00926,0.00450,0.0051,0.8081,0.9340 -1.750,-0.1236,0.00957,0.00459,0.0001,0.8016,0.9738 -1.500,-0.0619,0.00963,0.00441,-0.0068,0.7945,0.9962 -1.250,-0.0299,0.00958,0.00420,-0.0079,0.7868,1.0000 -1.000,-0.0065,0.00956,0.00405,-0.0072,0.7789,1.0000 -0.750,0.0179,0.00957,0.00394,-0.0067,0.7711,1.0000 -0.500,0.0418,0.00958,0.00384,-0.0060,0.7640,1.0000 -0.250,0.0671,0.00961,0.00380,-0.0057,0.7562,1.0000 0.000,0.0913,0.00965,0.00374,-0.0049,0.7495,1.0000 0.250,0.1171,0.00970,0.00375,-0.0047,0.7417,1.0000 0.500,0.1415,0.00976,0.00372,-0.0039,0.7353,1.0000 0.750,0.1676,0.00983,0.00377,-0.0037,0.7273,1.0000 1.000,0.1921,0.00990,0.00377,-0.0030,0.7210,1.0000 1.250,0.2182,0.00997,0.00384,-0.0027,0.7123,1.0000 1.500,0.2429,0.01004,0.00387,-0.0019,0.7049,1.0000 1.750,0.2685,0.01010,0.00392,-0.0015,0.6957,1.0000 2.000,0.2939,0.01016,0.00398,-0.0009,0.6867,1.0000 2.250,0.3184,0.01021,0.00398,0.0000,0.6783,1.0000 2.500,0.3443,0.01025,0.00406,0.0005,0.6675,1.0000 2.750,0.3698,0.01029,0.00413,0.0011,0.6571,1.0000 3.000,0.3950,0.01031,0.00416,0.0018,0.6464,1.0000 3.250,0.4200,0.01033,0.00416,0.0026,0.6356,1.0000 3.500,0.4456,0.01033,0.00423,0.0033,0.6229,1.0000 3.750,0.4711,0.01032,0.00426,0.0040,0.6090,1.0000 4.000,0.4965,0.01030,0.00428,0.0047,0.5938,1.0000 4.250,0.5225,0.01028,0.00435,0.0053,0.5748,1.0000 4.500,0.5480,0.01026,0.00440,0.0060,0.5536,1.0000 4.750,0.5737,0.01027,0.00448,0.0066,0.5268,1.0000 5.000,0.5990,0.01033,0.00450,0.0073,0.4782,1.0000 5.250,0.6224,0.01096,0.00458,0.0078,0.3480,1.0000 5.500,0.6445,0.01242,0.00529,0.0076,0.2045,1.0000 5.750,0.6643,0.01456,0.00656,0.0074,0.0592,1.0000 6.000,0.6856,0.01626,0.00815,0.0081,0.0320,1.0000 6.250,0.7077,0.01736,0.00934,0.0088,0.0276,1.0000 6.500,0.7271,0.01890,0.01092,0.0098,0.0252,1.0000 6.750,0.7447,0.02106,0.01312,0.0112,0.0241,1.0000 7.000,0.7659,0.02267,0.01484,0.0125,0.0238,1.0000 7.250,0.7872,0.02467,0.01703,0.0137,0.0236,1.0000 7.500,0.8085,0.02668,0.01927,0.0149,0.0233,1.0000 7.750,0.8294,0.02824,0.02110,0.0159,0.0220,1.0000 8.000,0.8481,0.03064,0.02383,0.0171,0.0215,1.0000 8.250,0.8634,0.03399,0.02760,0.0185,0.0219,1.0000 8.500,0.8741,0.03799,0.03200,0.0198,0.0228,1.0000 8.750,0.8847,0.04283,0.03705,0.0208,0.0246,1.0000 16.250,0.6077,0.18140,0.17801,-0.0282,0.0340,1.0000 16.500,0.6093,0.18445,0.18106,-0.0302,0.0339,1.0000